Missile pneumatic de-ballasting mechanism



Nov. 20, 1962 A. B. LEAMAN ETAL 3,064,538

MISSILE PNEUMATIC DE-BALLASTING MECHANISM Filed Sept. 13, 1961 LEO M GILADETT wot ATTORNEYS 3,54,538 Patented Nov. 120, 1952 3,064,538 MISSILE PNEUMATIC DE-BALLASTDJG MECHANISM Audley B. Leaman and Leo V. Giladett, Santa Cruz,

Califi, assiguors, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Sept. 13, 1961, Ser. No. 137,929 3 Claims. (Cl. 89-1.7)

This invention relates to a device for detonating an explosive propellant and, more particularly, to a detonator which is mechanically actuated and incorporates a delayed action feature.

In many armament systems, especially of the self-contained type, it is important to initiate a gas propellant system for moving an element by means which are simple, safe and yet positive. A typical means of generating such a gas propellant is to detonate an explosive charge and direct the gases generated therefrom under pressure against the element to be moved. A common method of igniting such a charge is by the familiar primer charge and striking hammer method whereby a hammer is propelled against a primer charge which detonates and in turn detonates the main propulsive charge. The present invention relates to a simple means for generating such a propulsive gas simply by means of cocking a hammer against a spring. The system may, further, incorporate a timing feature by simply inserting a delay column between the primer charge and the main gas generating charge. This delay column may be set to a pre-determined interval of time. Such a cocking-hammer ignition is particularly apt in a system'involving large moving masses, such as a projectile during launching. One peculiar advantage in this environment is the elimination of any power package within the armament system to cook the hammer and thereby generate the gas propellant. This may be accomplished simply by connecting the hammer to the mass away from which the armament package moves, e.g. the launching platform. Thus, a saving in power components and elimination thereof is accomplished by virtue of simply using a miniscule portion of the motive force separating the masses.

An object of the invention is to provide an improved charge igniter to eliminate ignition power components.

Another object is to provide a charge igniter which is actuable by the simple mechanical displacement of a small mass.

A further object of the invention is to provide a gaspropellant-actuating system with a simple, fail-safe, mechanical actuator.

Yet another object of the invention is to provide a charge igniter of the cocked-hammer type.

Still a further object is to provide a mechanical hammer igniter with the safety feature of a hammer-retaining ring which makes it impossible for the hammer to strike without the application of a cocking force, averting accidental striking.

A still further object is the provision of a wholly mechanical, lower power device for actuating a detonator on a missile.

A still further object is to provide a detonator delayingly actuated by the mere motion of the missile and dispensing with any power package on the missile.

A further object is to provide a lanyard detonator on a missile having a simple spring adjustment and a safety lock thereon.

Yet another object is to provide a detonator which is actuated by the uplift of the missile and which will provide for a delayed action ejection of a package from the missile at a specified time thereafter.

Yet another object is to provide a detonator which requires no power source for operation, and is mechanically actuated.

In the accompanying drawing FIG. 1 is a cross sectional schematic view of a missile under ejection from its submarine platform showing the lanyard actuated, membrane-piercing arrow.

FIG. 2 is a cross-sectional view of the pin-pulling and detonating assembly.

FIG. 3 is a cross sectional view of a modified portion of the pin-pulling assembly in FIG. 2 wherein the safety retaining ring has been added.

In the illustrated embodiment of the invention shown in FIG. 1, the lanyard-actuating detonator is shown in a typical missile environment. Here the detonator is used to propel a spear shown at 5 against a membrane 4 to release a pressurized gas contained within chamber C within missile 3. In this particular instance, the pressurized gas is used to eject ballast water W disposed within the chamber 8 of the missile 3 and reduce the mass of the projected missile. Here, the lanyards are shown in pairs at 7 and inter-connect the detonating chambers 9 with the platform 7a of a conventional submarine 1 when the missile 3 is propelled out of the submarine launching tube L after the launch door 2 has been opened. It will be understood that another type of launching platform, if desired, could be employed. These detonating chambers 9 incorporate the cocked-hammer detonating system of the present invention which includes a hammer and a pulldown rod. The hammers of the present invention are cocked by reason of the tie-down between lanyards 7 and the pull-down rod which pull the hammer or firing pin downward against its cocking spring upon the uplift of the missile 3 within the launching tube L and away from platform 7a until the releasable joint of the hammer and rod are moved an amount sufiicient to be disengaged, whereupon the hammer is released. As the hammer is released, the spring forcibly moves the hammer into firing engagement with the primer charge which in turn detonates a main charge after a predetermined delay. This delay may be pre-set according to the distance downrange at which the movable member, in this case the piercing spear 5 is to be actuated. When the main charge detonates a sufiicient amount of gas pressure is generated in the detonation chamber to forcibly move the piercing arrow 5 into engagement with the membrane 4 of chamber C, thereby rupturing the membrane and thus releasing the pressurized de-ballast gases from chamber C. The above is merely an illustrative embodiment of a mechanically actuated detonator and does not begin to exhaust the possible applications of the instant invention. The invention is apt for any environment where it is useful to initiate an explosive propulsion force simply by means of cocking a firing hammer.

In FIG. 2 there is shown, in cross sectional view the entire charge and detonator system of the instant invention. The main charge to be detonated and thereby evolve the propulsive gases is designated at 21, charge 21 is arranged to generate and propel its gases outwardly past plug 22 upon its ignition by flash charge 20 located at the other end of the firing chamber. Flash charge 20 is in turn ignited by the explosion of primer charge 12. However, the interval of time between primer ignition and' flash charge ignition may be varied by means of the delay column cartridge shown at 19. This delay column will allow a delayed actuation and evolution of the propulsive gases so that the driven member in the system may be actuated at a given interval of time after the detonating force has been set in motion. As seen above in the illustrated application, this delay interval is useful for providing an interval between the detonating force set in motion at the moment of launch and the time at which the spear'5 is to be actuated while the missile is airborne. Delay column cartridge 19 is provided with a plug 18 at the end facing primer 12. This plug provides access from the primer gases into the delay column. This firing pin or hammer 16 is the only moving element in the system and the element whose displacement is the cause of the whole explosive reaction, much in the manner of a firing pin being cocked in a gun. Spring 16, which is fixedly mounted in housing 14 and compressed under the action of the displacement of firing pin in the direction of the pulling force at its outer end, so as to be in a position to thrust the firing pin 10 against the primer charge 12 to detonate it. Pin head 24 is flanged to seat thespring 16. The exact point of displacement at which the hammer is released is determined by the excursion outwardly of the flanged members 25 and 26 which automatically separate and release the firing pin when they reach the other end 27 of the housing 14. The outward displacement of these flange members is kept in alignment by a guide 15, channeling their movement axially. The actuating force such as the lanyard shown at 7 in FIG. 1 is attached to the base of the grip so as to pull the joints 25 and 26 outwardly allowing for the eo'ckingof the firing pin 10. The distance of firing pin displacement may be arranged by adjusting the distance of displacement of the end of flanged member 26 from its rest point, as shownin the drawing, 'to the outer end 27 of housing 14 The provision of shims, o'r guides of adjustable length, in the housing is one means ofadjusting this pin displacement distance. This displacement distance further determines the striking force upon detonation since it is the only adjustable barometer for determining thedegree of compression of the spring 16. A safety pin 47 is provided to lock the firing pin and cocking assembly against accidental actuation, for instance, during transit and handling of the missile in the embodiment in FIG. 1. Pin 47 may take the form of a cotter pin as illustrated.

A further safety lock is provided in the modification shown in FIG. 3. F163 illustrates a modified version of the detonator and charge combination in FIG. 2 wherein the firing pin is prevented from accidental release and the initiation of an accidental explosion by means of a retaining ring 35. Thus, the retaining ring provides a safety lock for the firing pin 10. Unlike the safety pin 47 seen in FIG. 2, this safety provision is one that is fail-safe in that it'cannot be removed except by a direct orderto fire. This results by'virtue of the fact that the retaining ring locks the firing pin against any motion towards the primer charge 12 until there has been a motion in the cocking direction, away from primer charge 12, which motion expands the retaining ring and dislocates it out of the firing path of the firing pin 1%). Thus is provided a safety lock against all movements except the detonating movement. combination comprises the retaining ring proper35 which is an expandable annulus closely surrounding a section 36 of the firing-pin head 39 which is inset and grooved to correspond to the inner periphery of the retaining ring 35. Surrounding the outer periphery of this retaining ring 35 is an an'nular'groove 38cutin'to the housing 14 and inset deeply enough so as to allow the ring to be expanded to a diameter larger than the diameter of head 39 and thereby allow the firing-pin head 39 to pass in the firing direction. This latter movement is accomplished only when the firing pin is pulled axially, in the cocking direction and away from primer 12, expanding retaining ring 35 radially by virtue of lip 40 on the seating portion 36 of the firing pin 10. Being of a resilient metal material the retaining ring 35 will expand outwardly into annular recess 38 until lip 40 has passed its midpoint, at which point retaining ring 35 will snap back into the smaller annular grooved portion 37 of firing pin 10 and there remain to allow the movement The safety lock 4 of head 39 in the firing direction. Flange 41 prevents the retaining ring 35 from moving beyond this grooved inset. It will be noticed that enlarged head 39 on the firing pin 10 corresponds to a similar head portion 24, FIG. 2, and, like 24, is usedto seat and retain the firing spring 16.

As the illustration points out, the above cocked-hammer detonator has utility in actuating a movable element such as the spear 5 in a projected armament package such as the missile shown. This is especially true when used in combination with the retaining ring lock. However, this missile environment is only illustrative of the broad utility of the invention and'shouldnot obscure the fact that many otherapplications would be apt Wherever the separationof two rnasse's couldbeutilizedto'cock a hammer and gaseously actuate a member in one of the masses thereby dispe'nsir'ig'with a separate actuating signal means and actuator power package. One such'application would'be to m'ovea control element upon the separation of two bodies in outer space. Further, the very separation of the bodies in a missile package could be accomplished' by" merely" cocking the hammer on lift-oh and providing a' suitable delay column so that the explosive gases could effect the separ'ationof stages at a suitable moment. Still another like application would be in a submarine'torpedo whose ejection could cock the hammer and provide detonation after a suitable interval. Here, too, the safety retainer ring would make it impossible for the hammer to strike accidentally, being cleared only by the pulling-action torpedo ejection. A myriad of otheranalogous applications will suggest themselves to those skilled in this art.

It will be understood that various changes in the details, materials and arrangements" of parts which have been herein described and illustrated in order'to explain the nature of the invention, may be made by those skilled in the art within the principle and scope" of the invention as expressed in the appended claims.

What is claimed is:

1; Thecomb'ination ofa weapon system having a time d'elay'device for initiatingia missile pneumatic tie-ballasting mechanism, said combination comprising a missile launchingtube, a missile including a pressurized gas chamber contained within and movable through said tube, a frangible membrane for'closing said chamber, a platform disposed within said tube, spear means responsive to gas pressure for rupturing said frangible membrane and releasing said'pressurizedg'as from the chamber, a normally locked firingmech'anism carried by the missile, lanyard means connected to said firing mechanism and to said platform for actuating the firing mechanism from an initial position to a firing release position when the missile moves a predetermined amount with respect to the platform, gas pressure generating means for actuating said spear, means including a delay element for initiating said gas pressure generating means in time delay relation with respect to actuation of the firing mechanism, means fired'by said fir ing mechanism for initiating said delay element, and means. in communication with the gas generation means and the spear for supplying said gas pressure thereto.

2.. The combination of a weapon system having a time delay device for initiating a missile pneumatic de-ballasting mechanism, said combination comprising a missile launching tube, a missile including a pressurized gas chamber contained within and movable through said tube, a frangible membrane for closing said chamber, a platform disposed within said tube, a spear responsive to gas pressure for rupturing said frangible membrane and releasing the pressurized gas as the spear is forcibly driven into enengagement with the membrane, a firing pin movable from an initial position to a release position, an actuating rod in interlocking engagement with said firing pin for moving the firingpin from said initial position to said release position when the actuating rod is moved a predetermined amount, lanyard means connected to the firing pin and to said platform for moving the actuating rod said predetermined amount when the missile moves a predetermined amount with respect to the platform, gas pressure generating means for actuating said spear, a time delay element for initiating said gas pressure generating means when a predetermined period of time has elapsed, primer means fired by the firing pin as the firing pin is released and forcibly moved into engagement with said primer means for initiating said delay element, means for forcibly moving the firing pin into firing engagement with said primer means, and means communicating with the gas generation means and the spear for supplying said gas pressure thereto as the gas pressure generating is initiated.

3. The combination of a weapon system having an explosive actuated device for initiating a missile pneumatic de-ballasting mechanism, said combination comprising a launching tube, a missile supported Within said launching tube and having a pressurized gas container carried thereby, a frangible membrane for closing said container, a pressure responsive spear for rupturing said frangible membrane and releasing said pressurized gas, a housing having an explosive chamber, a main charge for generating said pressure as the charge is fired, a conduit in the housing connecting said explosive chamber and said spear for supplying said pressure thereto, an igniter charge for igniting said main charge, a delay charge for igniting igniter charge when a predetermined period of time has elapsed, a primer chamber in the housing, a primer charge disposed within said primer chamber for initiating said delay charge as the primer charge is fired, a hammer chamber disposed within said housing, a normally locked hammer in said chamber and having a striking head movable into firing engagement with the primer charge when the hammer is moved from an initial position to a release position, spring means in said hammer chamber in engagement with the hammer for forcibly moving the hammer and driving the striking head in firing engagement with the primer charge as the hammer is released, an actuating pin in interlocking engagement with the hammer for moving the hammer from an initial position to a release position, sleeve means on the housing for maintaining the actuating pin in interlocking engagement with the hammer until said actuating pin is moved a predetermined amount, means secured to said actuating pin and the tube for moving the actuating pin said predetermined amount as the missile moves within said tube, a retaining collar on the hammer and of a diameter substantially equal to the diameter of the hammer chamber, said collar having a first annular groove disposed adjacent the striking head, a cooperating groove in the housing and normally in alignment with the first groove in the collar, said collar having an additional annular groove of a diameter substantially less than the diameter of said first annular groove, and an expansible ring normally disposed within said first annular groove and the cooperating groove in the housing for maintaining the hammer in an initial safe position, said ring being movable into the cooperating groove to allow the hammer to be moved to said release position and thereafter into the additional groove to allow the hammer to be moved from said release position to said firing position.

References Cited in the file of this patent UNITED STATES PATENTS 2,132,148 Davis Oct. 4, 1938 2,581,645 Frieder et al. Jan. 8, 1952 2,732,153 Frieder et al. Jan. 24, 1956 2,804,804 Cumming Sept. 3, 1957 2,857,845 Seavey Oct. 28, 1958 2,873,048 Musser Feb. 17, 1959 

